CN212401602U - Seesaw type rotor wing fatigue test device - Google Patents
Seesaw type rotor wing fatigue test device Download PDFInfo
- Publication number
- CN212401602U CN212401602U CN202020755794.3U CN202020755794U CN212401602U CN 212401602 U CN212401602 U CN 212401602U CN 202020755794 U CN202020755794 U CN 202020755794U CN 212401602 U CN212401602 U CN 212401602U
- Authority
- CN
- China
- Prior art keywords
- wire rope
- steel wire
- rotor
- unit
- test
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model provides a seesaw formula rotor fatigue test device, the device include the frame element and fix at the inside fixed unit of oar root of frame element, exciting force unit and centrifugal force unit. The test motor drives the eccentric wheel to rotate after rotating speed adjustment is carried out through the frequency converter, and drives the excitation box through the link mechanism, so that the excitation box can generate flapping moment and shimmy moment loads under various working conditions of the simulation rotor wing according to test input requirements; meanwhile, centrifugal force is applied through the chain block, and the centrifugal force is transmitted to the steel wire rope pulley block through the steel wire rope connecting rod mechanism and then transmitted to the blade test piece; and finally, monitoring the amplitude of each channel of the section by a dynamic strain measurement system to obtain corresponding data of a rotor wing fatigue test. The utility model discloses seesaw formula rotor to gyroplane commonly used designs, has simple structure, advantages such as convenient to use is reliable.
Description
Technical Field
The utility model provides a seesaw formula rotor fatigue test device relates to seesaw formula rotor and paddle fatigue test technique, is applicable to rotor paddle fatigue test and gyroplane airworthiness field.
Background
In the flight process of the rotor type aircraft, the rotor bears the complex alternating load effect, the fatigue problem is very prominent, and the safety, reliability and economy of the rotorcraft are directly influenced. The seesaw type rotor wing is suitable for the gyroplane, and the seesaw type rotor wing fatigue test is an important basis for the gyroplane to obtain evidence for airworthiness and the rotor wing to be in fixed life.
At present, most of rotor fatigue tests are devices for helicopter rotor fatigue tests, and the common characteristics of the devices are that the rotor fatigue test system and the devices are too complex due to the complex working condition of the helicopter rotor, the manufacturing cost and the test cost are too high, and the manufacturing period and the test period are very long. And too complicated system leads to each simulation load part to have great mutual interference in rotor fatigue test, leads to rotor fatigue test result and decide the life analysis inaccurate, directly influences the test result.
Therefore, the conventional rotor fatigue testing device has the following defects:
1. the design of the test device is complex;
2. the manufacturing cost and the test cost are high, and the period is long;
3. because of the defects, the traditional rotor wing fatigue test device is not suitable for rotor wing fatigue test and blade life-fixing analysis in the process of aeronautical evidence collection of the gyroplane.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a solve prior art's problem, provide a seesaw formula rotor fatigue test device, design to the common seesaw formula rotor of gyroplane, have simple structure, advantages such as convenient to use is reliable.
The utility model provides a seesaw formula rotor fatigue test device, including the frame element and fix fixed unit of oar root, exciting force unit and the centrifugal force unit inside the frame element.
The propeller root fixing unit consists of an annular groove flange plate and an inclined plane plate, the annular groove flange plate is connected with the rotor hub and the inclined plane plate, and the blade test piece is arranged in the middle of the annular groove flange; the inclined plane plate is connected with the annular ring flange and the frame unit, and the pre-cone angle of the seesaw type rotor wing is simulated and counteracted.
The centrifugal force unit provides a centrifugal force load under a simulated real working condition and comprises a chain block, a force sensor, a steel wire rope connecting rod mechanism and a steel wire rope pulley block which are sequentially connected, wherein the chain block and the steel wire rope connecting rod mechanism are fixedly connected with the frame unit, and the steel wire rope pulley block is connected with the exciting force unit.
The excitation force unit simulates flapping moment and shimmy moment loads borne by the rotor under various working conditions and comprises an excitation box, a connecting rod mechanism, an eccentric wheel and a test motor with a frequency converter, which are connected in sequence, wherein the excitation box is connected with a steel wire rope pulley block.
The steel wire rope connecting rod mechanism is further improved and consists of a base, a supporting strip and a connecting box section which are sequentially connected, the base is installed on the frame unit through bolts and is connected with the connecting section box through the supporting strip, and the connecting section box is simultaneously connected with the force sensor and the steel wire rope pulley block. The steel wire rope connecting rod mechanism is provided with a ball bearing, and the ball bearing controls the steel wire rope connecting rod mechanism to rotate in a vertical plane.
In a further improvement, the frame unit comprises a test frame and a plurality of inclined support structures for fixing the test frame.
The vibration excitation box is further improved, vibration excitation box baffles are arranged on two sides of the vibration excitation box, and vertical limiting is carried out on the vertical reciprocating motion of the vibration excitation box.
In a further improvement, a protective net is arranged outside the frame unit.
The utility model also provides a seesaw formula rotor fatigue test device's operating method, including following step:
1) the test frame is fixed on the ground, the paddle test piece is installed in the paddle root fixing unit, the corresponding strain gauge is attached to the paddle test piece according to requirements, and the paddle test piece is externally connected with a dynamic strain measurement system.
2) The test motor drives the eccentric wheel to rotate after rotating speed adjustment is carried out through the frequency converter, and the vibration box is driven through the link mechanism, so that the vibration box can generate flapping moment and pendulum vibration moment loads under various working conditions of the simulation rotor wing according to test input requirements.
3) Meanwhile, centrifugal force is applied through the chain block, the magnitude of the centrifugal force is measured through a force sensor connected between the chain block and a steel wire rope connecting rod mechanism, the centrifugal force is transmitted to a steel wire rope pulley block through the steel wire rope connecting rod mechanism and then transmitted to the paddle test piece, the steel wire rope connecting rod mechanism enables the connecting rod mechanism to rotate in a vertical plane through installing a ball bearing, the vibration amplitude of the end portion of the paddle test piece, which is transmitted to the force sensor and the chain block, is effectively weakened, and the influence on experiment safety and load simulation is avoided.
4) And monitoring the amplitude of each channel of the section by using a dynamic strain measurement system to obtain corresponding data of a rotor wing fatigue test.
The utility model has the advantages that:
1. the utility model designs the rotor fatigue device aiming at the seesaw type rotor of the gyroplane, has relatively simple structure, convenient and reliable use, convenient disassembly and replacement of easy fatigue parts or parts, can collect various strain values of the rotor, and records the cycle times and the test process;
2. can realize rotor centrifugal force load simulation and input through chain block, wire rope link mechanism to the effectual vibration of avoiding paddle test piece tip arouses after transmitting on force sensor and the chain block to swing by a wide margin, causes the influence to experimental security and load simulation.
3. The inclined plane board in the propeller root fixing unit can realize the offset of the rotor wing pre-cone angle, so that the rotor wing blades are in a horizontal state in a test, the position of the test design load application is convenient, and the fixed support boundary condition of the rotor wing of the rotorcraft during normal flight can be simulated.
Drawings
FIG. 1 is a main body diagram of the seesaw type rotor wing fatigue test device of the utility model;
in the figure, a paddle root fixing unit 1, an excitation box 2, an excitation box baffle 3, a test motor 4, a force sensor 5, a chain block 6, an eccentric wheel 7, a test frame 8, an inclined support 9, a frequency converter 10, a link mechanism 11, a steel wire rope pulley block 12, a steel wire rope link mechanism 13 and a paddle test piece 14.
Fig. 2 is a schematic view of a blade root fixing unit 1 of the present invention;
in the figure, a ring groove flange 15 and a bevel plate 16.
Fig. 3 is a schematic view of the wire rope link mechanism 13 of the present invention;
in the figure, the base 17, the support strip 18, the connection box 19.
FIG. 4 is a schematic diagram of an exciting force unit of the present invention;
in the figure, an excitation box 2, an excitation box baffle 3, a test motor 4, an eccentric wheel 7, a link mechanism 11, a steel wire rope pulley block 12 and a blade test piece 14 are arranged.
Detailed Description
The present invention will be further explained with reference to the accompanying drawings.
The propeller root fixing unit 1 is used for fixing a propeller root part of a test piece propeller blade of the test device and simulating the real installation situation of the seesaw type rotor wing propeller root.
The excitation box 2, the test motor 4, the eccentric wheel 7, the frequency converter 10 and the link mechanism 11 jointly form an excitation force unit of the test device, and are used for simulating flapping moment and shimmy moment loads borne by the rotor under various working conditions in a test, as shown in fig. 4, wherein the excitation box 2, the link mechanism 11, the eccentric wheel 7 and the test motor 4 with the frequency converter are sequentially connected, and the excitation box 2 is connected with the steel wire rope pulley block 12.
The force sensor 5, the chain block 6, the steel wire rope pulley block 12 and the steel wire rope link mechanism 13 jointly form a centrifugal force unit of the test device, and the centrifugal force unit is used for simulating and recording the centrifugal force applied to the blades in the rotation of the rotor wing in the test.
The vibration excitation box baffles 3 are positioned on two sides of the vibration excitation box 2 and used for limiting vertical reciprocating motion of the vibration excitation box 2 in a test and preventing the vibration excitation box from deflecting due to the motion.
The test frame 8 and the inclined supports 9 jointly form a frame unit of the test device, and the frame unit is used for splicing the whole test device to enable each part to play respective roles.
The blade test piece 14 is a test piece of the test device.
As shown in FIG. 2, the blade root fixing unit 1 is a schematic diagram and consists of a ring groove flange 15 and an inclined plane plate 16, and a blade test piece is arranged in the middle of the ring groove flange 15. The ring channel flange 15 is used for connecting the rotor hub and the bevel board, and the rotor can carry out angle modulation. The ramp 16 is used to simulate and cancel the pre-cone angle of the actual see-saw rotor, leaving the blade level. Meanwhile, the inclined plane plate 16 is also connected with the annular groove flange 15 and the test frame 8 and bears the action of centrifugal force. The steel wire rope connecting rod mechanism is provided with a ball bearing, and the ball bearing controls the steel wire rope connecting rod mechanism to rotate in a vertical plane.
Fig. 3 is a schematic view of a wire rope link mechanism 13, which is composed of a base 17, a support strip 18 and a connection box section 19, and is used for preventing the vibration at the end of the blade test piece 14 from being transmitted to the force sensor 5 and the chain block 6 to cause large-amplitude swing, and thus, the influence on the experimental safety and the load simulation is avoided. The base is mounted on the test frame 8 by bolts and is connected with a connecting section box 19 by a support strip 18, and the connecting section box 19 is simultaneously connected with the force sensor 5 and the steel wire rope pulley block 12.
The utility model discloses concrete theory of operation does:
the fatigue test device is fixed on the ground through a test frame 8, a blade test piece 14 is installed on the blade root fixing unit 1, and the corresponding strain gauge is attached to the blade (and the hub) according to requirements and is externally connected with a dynamic strain measurement system.
The test motor 4 drives the eccentric wheel 7 to rotate after rotating speed adjustment is carried out through the frequency converter 10, and drives the excitation box 2 through the link mechanism 11, so that the excitation box can generate flapping moment and shimmying moment loads under various working conditions of the simulation rotor wing according to test input requirements.
Simultaneously, centrifugal force is applied through the chain block 6, the size of physical force is measured through the force sensor 5 connected between the chain block 6 and the steel wire rope connecting rod mechanism 13, the centrifugal force is transmitted to the steel wire rope pulley block 12 through the steel wire rope connecting rod mechanism 13 and then transmitted to the paddle test piece 14, the steel wire rope connecting rod mechanism 13 is provided with a ball bearing through installation, so that the connecting rod mechanism can rotate in a vertical plane, the vibration amplitude of the end part of the paddle test piece 14, transmitted to the force sensor 5 and the chain block 6, and the influence on experimental safety and load simulation is avoided.
Finally, based on the above, the amplitude of each channel of the profile can be monitored by a dynamic strain measurement system, and corresponding data of the rotor fatigue test can be obtained.
The utility model discloses the concrete application way is many, and the above-mentioned only is the preferred embodiment of the utility model, should point out, to ordinary skilled person in this technical field, under the prerequisite that does not deviate from the utility model discloses the principle, can also make a plurality of improvements, and these improvements also should be regarded as the utility model discloses a scope of protection.
Claims (6)
1. The utility model provides a seesaw formula rotor fatigue test device which characterized in that: the device comprises a frame unit, and a paddle root fixing unit, an exciting force unit and a centrifugal force unit which are fixed in the frame unit;
the propeller root fixing unit consists of an annular groove flange plate and an inclined plane plate, the annular groove flange plate is connected with the rotor hub and the inclined plane plate, and the blade test piece is arranged in the middle of the annular groove flange; the inclined plane plate is connected with the annular ring flange and the frame unit, and the pre-cone angle of the seesaw type rotor wing is simulated and counteracted;
the centrifugal force unit provides a centrifugal force load under a simulated real working condition and comprises a chain block, a force sensor, a steel wire rope connecting rod mechanism and a steel wire rope pulley block which are sequentially connected, wherein the chain block and the steel wire rope connecting rod mechanism are fixedly connected with the frame unit, and the steel wire rope pulley block is connected with the exciting force unit;
the excitation force unit simulates flapping moment and shimmy moment loads borne by the rotor under various working conditions and comprises an excitation box, a connecting rod mechanism, an eccentric wheel and a test motor with a frequency converter, which are connected in sequence, wherein the excitation box is connected with a steel wire rope pulley block.
2. A teeterboard rotor fatigue test apparatus as defined in claim 1, wherein: the steel wire rope connecting rod mechanism is composed of a base, a supporting strip and a connecting box section which are sequentially connected, the base is installed on the frame unit through bolts and is connected with the connecting box through the supporting strip, and the connecting box is simultaneously connected with the force sensor and the steel wire rope pulley block.
3. A teeterboard rotor fatigue test apparatus as claimed in claim 1 or claim 2, wherein: the steel wire rope connecting rod mechanism is provided with a ball bearing, and the ball bearing controls the steel wire rope connecting rod mechanism to rotate in a vertical plane.
4. A teeterboard rotor fatigue test apparatus as defined in claim 1, wherein: the frame unit comprises a test frame and a plurality of inclined support structures for fixing the test frame.
5. A teeterboard rotor fatigue test apparatus as defined in claim 1, wherein: and vibration excitation box baffles are arranged on two sides of the vibration excitation box and vertically limit the up-and-down reciprocating motion of the vibration excitation box.
6. A teeterboard rotor fatigue test apparatus as defined in claim 1, wherein: and a protective net is arranged on the outer side of the frame unit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020755794.3U CN212401602U (en) | 2020-05-07 | 2020-05-07 | Seesaw type rotor wing fatigue test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020755794.3U CN212401602U (en) | 2020-05-07 | 2020-05-07 | Seesaw type rotor wing fatigue test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212401602U true CN212401602U (en) | 2021-01-26 |
Family
ID=74376043
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020755794.3U Active CN212401602U (en) | 2020-05-07 | 2020-05-07 | Seesaw type rotor wing fatigue test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212401602U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111645877A (en) * | 2020-05-07 | 2020-09-11 | 南京华航翼飞行器技术有限公司 | Seesaw type rotor wing fatigue test device and working method thereof |
| CN113670739A (en) * | 2021-08-17 | 2021-11-19 | 无锡瑞来检测科技有限公司 | Helicopter main rotating blade fatigue test device |
-
2020
- 2020-05-07 CN CN202020755794.3U patent/CN212401602U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111645877A (en) * | 2020-05-07 | 2020-09-11 | 南京华航翼飞行器技术有限公司 | Seesaw type rotor wing fatigue test device and working method thereof |
| CN113670739A (en) * | 2021-08-17 | 2021-11-19 | 无锡瑞来检测科技有限公司 | Helicopter main rotating blade fatigue test device |
| CN113670739B (en) * | 2021-08-17 | 2024-04-26 | 无锡瑞来新材料科技有限公司 | Helicopter main rotor blade fatigue test device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN212401602U (en) | Seesaw type rotor wing fatigue test device | |
| CN109977448B (en) | Rotor wing aerodynamic load analysis method based on actual measurement structure load | |
| KR100913667B1 (en) | Helicopter Tail Rotor Test Rig | |
| US5140856A (en) | In situ balancing of wind turbines | |
| EP3237873B1 (en) | Fatigue testing | |
| EP2728332B1 (en) | Test rig | |
| CN111645877A (en) | Seesaw type rotor wing fatigue test device and working method thereof | |
| CN109632249B (en) | Wing type high-speed wind tunnel dynamic test device | |
| Donham et al. | Ground and Air Resonance Characteristics of a Soft In‐Plane Rigid‐Rotor System | |
| CN106441902B (en) | A kind of sub- scale simulation aero-engine rotation test device and test method | |
| CN103512715A (en) | Nacelle test apparatus | |
| Kreshock et al. | Overview of the tiltrotor aeroelastic stability testbed | |
| CN104198152A (en) | Bionic flapping wing aircraft lifting force test device and method | |
| EP2674740A1 (en) | A fatigue testing device for a wind turbine blade | |
| CN113504039A (en) | Rotor wing structure static strength test method | |
| CN104713708B (en) | Main shaft fatigue experimental device | |
| CN112857719B (en) | Fixed airfoil flutter ground test device and method | |
| CN107764536A (en) | Propeller test device | |
| CN215178574U (en) | Rotor structure static strength test device | |
| CN108760260A (en) | A kind of fatigue experimental device and method for wind electricity blade load alternation pneumatic load | |
| RU2631557C1 (en) | Method of determination in flight of bending stresses on rotor shaft of helicopter with torsional rotor head | |
| CN106965953A (en) | A kind of Retracting Or Lowering Aerodynamic Loads On Landing Gear analogue means and its loading method | |
| CN115465472A (en) | Flapping wing aircraft testing device | |
| CN114590420A (en) | Vertical take-off and landing aircraft nacelle parameter testing device | |
| Thornburgh et al. | Structural Modeling and Validation of the TiltRotor Aeroelastic Stability Testbed |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |